F05D 2220/3219
For the last stage of a compressor or a high pressure compressor
Official title: for the last stage of a compressor or a high pressure compressor
F05D2220/3219 (For the last stage of a compressor or a high pressure compressor) appears on 111 US grants and 120 published applications in this corpus.
Search patents in F05D- Granted patents
- 111
- Published applications
- 120
- Assignees
- 32
- Inventors
- 308
- Latest grant
- 14 Jul 2026
Filings by year
| Year | Granted patents | Published applications |
|---|---|---|
| 2011 | 0 | 1 |
| 2012 | 1 | 2 |
| 2013 | 1 | 4 |
| 2014 | 3 | 3 |
| 2015 | 2 | 5 |
| 2016 | 4 | 17 |
| 2017 | 2 | 9 |
| 2018 | 7 | 6 |
| 2019 | 14 | 10 |
| 2020 | 15 | 15 |
| 2021 | 12 | 10 |
| 2022 | 19 | 7 |
| 2023 | 6 | 13 |
| 2024 | 7 | 6 |
| 2025 | 11 | 8 |
| 2026 | 7 | 4 |
By publication year. 2026 runs to 8 Oct.
Recent patents
- Forward load reduction structures for aft-most stages of high pressure compressors14 Jul 2026US 12,680,557 B2General Electric Company
- Gas turbine engine2 Jun 2026US 12,644,386 B2General Electric Company
- Aircraft engine impeller with exducer shroud forward sweep31 Mar 2026US 12,590,590 B2Pratt & Whitney Canada Corp.
- Hybrid shroud impeller10 Mar 2026US 12,571,409 B2Rtx Corporation
- Gas turbine engine compression system with core compressor pressure ratio20 Jan 2026US 12,528,592 B2ROLLS-ROYCE plc
- Compressor bleed slot diffuser30 Jul 2026US 2026/0218652 A1Pratt & Whitney Canada Corp.
- More compact aircraft propulsion system23 Jul 2026US 2026/0210297 A1Safran Aircraft Engines
- Hybrid shroud impeller25 Jun 2026US 2026/0177077 A1Rtx Corporation
- Gas turbine engine compression system with core compressor pressure ratio30 Apr 2026US 2026/0116550 A1ROLLS-ROYC plc
- Gas turbine engine compression system with core compressor pressure ratio2 Oct 2025US 2025/0304269 A1ROLLS-ROYCE plc
Most cited
By later US patents
- Multiple staged compressor with last stage airfoil cooling57US 8,858,161 B1Florida Turbine Technologies, Inc. · 2014
- Cooled cooling air system for a turbofan engine23US 10,794,288 B2Raytheon Technologies Corporation · 2020
- Single phase micro/mini channel heat exchangers for gas turbine intercooling19US 10,316,750 B2Rolls-Royce North American Technologies Inc. · 2019
- Rear hub cooling for high pressure compressor13US 8,459,040 B2United Technologies Corporation · 2013
- Active clearance control system and method for gas turbine9US 8,973,373 B2General Electric Company · 2015